Rudder-bar retainer



oct. 16,1928. 1,681,732

R. E.. MITTON RUDDER BAR nETAI NE1L Filed June 26, 1926 ters of reference indicate likeparts through- Patented oci. 16, 192s;

p y A"ROBERT, MITTON, "or sALTinAKE CITY, UTAH. i

nonnen-,Ban RETAINER.

" Application filed `.nine 2e,r

My invention relate-sto aeroplanes has Y. i, for its `object to provide a new and eiiicient rudder bar retainer.y i i A further object is ,tokprov-idei anewl rudder bar retainer whichV maybe set bythe operator at any desired angle or in a directline,

and, after the retaineris set, the yoperator may remove his leet to .rest them.

A still :further '.objectis toprovide a rudder retainer which will make the operation of an aeroplane against a side wind much easier and safer than has heretoiore been. possible and oney which will be easily operated and will not tire or tax the strength ofthe aviator.`

These and other objects I accomplish with the device illustrated in the accompanying drawings in which similar numerals and let out the several views and as described in the specifications forming a part of thisapphcation and pointed out in the appended claims.

In the drawings in which I have shown the best and most preferred manner of building my invention, Figure 1 is a Jfront view of the rudder bar of an aeroplane with my retaining device in place thereon. Figure 2 is a plan view of the same. Figure 3 is a plan view oi' the stand or support for the rudder bar and my retainer shown Vwithout the rudder barin place. Figure 4 isa diagrammatic plan view of the rudder bar andthe rudder, with my retainer in placethereon. Figure 5 is a plan view of oneof the pedals of myretainer. Figure 6 isa section 0n line 6 6 of Figure 5. 4 Y i In the drawings I have shown the rudder bar of the aeroplane as A, on k'the ends VSoif which bar the cables B, which operate the rudder C, are attached. kA spider frame l is constructed and' is centrally bored, as lat 2, to receive the pivot bolt 3 of the rudder bar B. The said spider 'l'raine 1 is secured to the iioor of the aeroplaneand is braced by the extending flange D. The outer edge 01""- the said spider is made in the shape of two arcs E of a circle and racks 4 and 4 arek secured on both sides of the spider arcs E, Levers 5 and, 6 are secured to the rudder bar.

' kA by the pivot pins 7 which pass throughone corner of said levers and leave the other'end of the said levers free to move. The saidA levers 5 and 6 are made in one piece and are bent at right angles on the line 8, as shown inrFigure 6, and again-at right angles, as at .9,so that oneportion 10 of said levers is par-A allel Withthe top portion 6. An extended ifeet from' thelevers 5 and 61 192s. sriai no. "Vlissing l lugporztio'nill isprovidedontheeXtreme; y

of ,the portioirl() yof said'levers and has va dog f ofatcilil on ,its extreme end thereof.. iWheIl kthe said `leversare securedtofl the rudder bar `Alby,thexpivot pins'the dog1s`12wvillbe en- 4sneed .with the teeth livnthe redis Land 455 f Y Spring holding flanges 114 are provided on the i,

otherxgendsofsaid leverspandiiandsprings; i j 15 and; 11,6.4 are secured therein and vhave their other endsisecured .to .the rudder bar Afby..

the bar y1f?,which is secured tosaid rudder bar A and which is bored on its .ends to receive thesaidsprings. The'said springs l5 and 16 vwhen engaged inthe iianges 14 and the fholesin the bar 17 hold the levers in the position shown in Figures 2 andi-3 and hold the dogs 12 in engagement with the teeth 13 .Y of the racks 4 and 4. The pivot pins f pass through thefupper and lower sides 6 and 10 of the said levers y5 and 6, as lshown in Figures 6, so that the Vlevers and 'dogs are pivoted `throughthe same point and the action of each vis at the saine time and is positive. Retaining flanges 20 are provided on the ends ofthe levers 5 and 6 opposite the spring flanges 14 to keep the foot of the operator from sliding therefrom.

The operation of my device is as follows:

Y .Vhen the operator of the aeroplane desires to set the rudder at any given `or desired point, using his Vfeet, he pushes the rudder bar A to the desired position and then releases his are removed the springs 15 and 16 will draw the levers toward the rear and the extended lugs 11.` withtheir dogs 12, will be moved toward theracls 4 and 4. The dogs 12fwill Should it be necessary to will placehis feet on the levers 5 and6 4and press th em. downwardly or forwardly andthe dogs 12 will be disengaged' from the teeth 13 on the racks and the rudder bar A may thus be moved to any desiredpositi'on. Should' there he astrong head wind from either side, the aviator will set the rudder bar A at such a position as will cause the aeroplane to go forward in the desired direction and may Then the feet then remove his feet from therudder bar A;

The dogs '12' will engage with'the rteeth 13 and the said rudder bar will be held in that" position. 4 As the rudder bar A isgconnectedk with the rudder C bythe cables Bkthe rudder` bar will at alltimes coact with the said ruding-'dogs forlnedin the lower and inner'fsid'egaged r"with said extensionsand with ysaid v rudder bar to normally hold said dogs in said` der and the sired. Y

Having thus described my invention I desire to secure by Letters Patent and claim:

l. In a rudder bar retainer the combination 1 of a rudderbar; a. frame upon which Said rudder bar is supported having an extended spider shaped framework-formed thereon, onfl the Outer and upper edge of which is provided 'an inwardly toothed'rack segmentl on each sidehof thefrarne; bellcrank oot'op-v erated levers pivoted on said rudder bar havthereof adapted to engagewith' the toothed "racks on said supporting frame; an extension .on the back side of said levers to' which one end of a spring is secured; and springs en- 20 toothed racks substantially as described.

plane will be controlled as de-y` Q. In arudder bar retainer the combination of a foot operated rudder vbar pivotally mounted on a supporting frame and having the operating wires secured on the free ends thereof; inwardly projeoting toothed racks supported below and upon which the outer ends of said rudderbar are supported; pivy ot'edlevers 0n thefarins of said rudder bar;

dogs integral with saidA levers, and to be opwhen-the operatosffeet are removed -frornI said levers and to press the dogs backy into` engagement after the 'rudder' `bar hasy been operated kand released. Iv f y In testimony whereof I have affixed my signature. y Y y `1 ROBERTE. MITTON'. 

